Battery state of charge compensation

Abstract

The power source includes: a battery defining a state of charge; a converter in electrical communication with the battery; and a controller in operable communication with the converter, the controller including a compensation trigger circuit configured to provide a compensation trigger value based on a power output of the battery; and a dynamic droop control circuit configured to receive the compensation trigger value and switch an output droop value of the dynamic droop control circuit from an upper output droop measurement value to a lower output droop measurement value, where the lower output droop measurement value is based on a state of charge of the battery.

Description

[0001] This application is a divisional application of the invention patent application filed on March 18, 2022, with application number 202210268588.3 and invention title "Battery State of Charge Compensation". Technical Field

[0002] This topic generally relates to state-of-charge compensators for batteries in electric systems, such as battery systems in hybrid electric aircraft propulsion systems. Background Technology

[0003] Some aircraft use electricity to power or supplement their propulsion systems, various aircraft payloads, or both. It is not uncommon for aircraft to include multiple batteries to provide or supplement this power. It is also not uncommon for the states of charge of the various batteries to differ during operation due to uneven charging, battery age, battery usage, and other factors.

[0004] Uneven state of charge (SCC) among batteries can lead to a loss of system performance. Systems and / or methods that reduce SCC unevenness among batteries would be useful. Summary of the Invention

[0005] Aspects and advantages of the invention will be set forth in part in the description which follows, or will be obvious from the description, or may be learned by practice of the invention.

[0006] In one exemplary embodiment of this disclosure, a power source is provided. The power source includes: a battery defining a state of charge; a converter electrically connected to the battery; and a controller operatively connected to the converter, the controller including: a compensation trigger circuit configured to provide a compensation trigger value based on the battery's power output; and a dynamic droop control circuit configured to receive the compensation trigger value and switch the output droop value of the dynamic droop control circuit from an upper output droop measurement value to a lower output droop measurement value, wherein the lower output droop measurement value is based on the battery's state of charge.

[0007] These and other features, aspects, and advantages of the invention will be better understood by reference to the following description and the appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention. Attached Figure Description

[0008] This specification sets forth a complete and practical disclosure of the invention, including its best mode, for those skilled in the art, with reference to the accompanying drawings, wherein:

[0009] Figure 1 This is a top view of an aircraft according to various exemplary embodiments of the present disclosure.

[0010] Figure 2 This is a schematic cross-sectional view of a gas turbine engine according to an exemplary embodiment of the present disclosure, which can be installed... Figure 1 On an exemplary aircraft.

[0011] Figure 3 This is a schematic cross-sectional view of an electric fan assembly according to an exemplary embodiment of the present disclosure, the electric fan assembly being installable... Figure 1 On an exemplary aircraft.

[0012] Figure 4 This is a top view of an aircraft including a propulsion system according to another exemplary embodiment of the present disclosure.

[0013] Figure 5 This is a close-up view of a power supply according to an exemplary embodiment of the present disclosure.

[0014] Figure 6 This is a schematic diagram of a power supply according to an exemplary embodiment of the present disclosure.

[0015] Figure 7 yes Figure 6 A close-up schematic diagram of the first controller of the power supply.

[0016] Figure 8 It is a lookup table according to an exemplary embodiment of the present disclosure.

[0017] Figure 9 This is a flowchart of the method for operating a power source. Detailed Implementation

[0018] Reference will now be made in detail to existing embodiments of the invention, one or more of which are illustrated in the accompanying drawings. The detailed description uses numbers and letters to refer to features in the drawings. In the drawings and description, similar or analogous reference numerals are used to refer to similar or analogous portions of the invention.

[0019] As used in this article, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another, rather than to indicate the location or importance of individual components.

[0020] The singular forms of “one,” “a,” and “the” include the plural, unless the context explicitly states otherwise.

[0021] The approximate language used herein throughout the specification and claims is applied to modify any quantitative expression that may allow for variation without altering the essential function associated therewith. Therefore, the value modified by one or more terms such as “about,” “approximate,” and “substantially” is not limited to the specified precise value. At least in some cases, the language of approximation may correspond to the precision of the instrument measuring the value, or the precision of the method or machine used to construct or manufacture the part and / or system. For example, the language of approximation may refer to a margin of 1, 2, 4, 5, 10, 15, or 20% of the endpoints of a single value, a range of values, and / or a range of defined values. Herein and throughout the specification and claims, scope limitations are combined and interchanged, and such scope is identified and includes all subscopes contained herein, unless otherwise indicated by context or language.

[0022] As used herein, the terms “processor” and “computer,” as well as related terms such as “processing device,” “computing device,” and “controller,” are not limited to those integrated circuits referred to in the art as computers, but rather refer more generally to one or more processing devices, including one or more of microcontrollers, microcomputers, programmable logic controllers (PLCs), application-specific integrated circuits, and other programmable circuits, and these terms are used interchangeably herein. In the embodiments described herein, the computer or controller may additionally include memory. This memory may include, but is not limited to, computer-readable media such as random access memory (RAM) and computer-readable non-volatile media such as flash memory. Alternatively, floppy disks, optical disc-read-only memory (CD-ROM), magneto-optical disc (MOD), and / or digital versatile optical disc (DVD) may also be used. Additionally, in the embodiments described herein, the computer or controller may include one or more input channels and / or one or more output channels. Input channels may be, but are not limited to, computer peripherals associated with an operating interface, such as a mouse and keyboard, or sensors, such as engine sensors associated with an engine (e.g., a gas turbine engine), for determining engine operating parameters. Furthermore, in exemplary embodiments, output channels may include, but are not limited to, an operating interface display. In addition, memory can store software or other instructions that, when executed by a controller or processor, allow the controller to perform certain operations or functions. The term "software" can include any computer program stored in memory, or any computer program accessible from memory for execution by, for example, a controller, processor, client, and server.

[0023] Referring now to the accompanying drawings, the same numbers throughout the figure represent the same elements. Figure 1 A top view of an exemplary aircraft 10 is provided, which may include various embodiments of this disclosure. For example... Figure 1As shown, the aircraft 10 defines a longitudinal centerline 14 extending through the aircraft 10, a lateral direction L, a front end 16, and a rear end 18. Furthermore, the aircraft 10 includes a fuselage 12 extending longitudinally from the front end 16 to the rear end 18 of the aircraft 10, and wing assemblies including port and starboard sides. More specifically, the port side of the wing assembly is a first, port wing 20, and the starboard side of the wing assembly is a second, starboard wing 22. The first wing 20 and the second wing 22 each extend laterally outward relative to the longitudinal centerline 14. The first wing 20 and a portion of the fuselage 12 together define a first side 24 of the aircraft 10, while the second wing 22 and another portion of the fuselage 12 together define a second side 26 of the aircraft 10. In the described embodiment, the first side 24 of the aircraft 10 is configured as the port side of the aircraft 10, and the second side 26 of the aircraft 10 is configured as the starboard side of the aircraft 10.

[0024] Each wing 20, 22 of the described exemplary embodiments includes one or more leading-edge flaps 28 and one or more trailing-edge flaps 30. The aircraft 10 further includes a vertical stabilizer 32 having rudder flaps (not shown) for yaw control, and a pair of horizontal stabilizers 34, each having elliptical flaps 36 for pitch control. The fuselage 12 also includes an outer surface or skin 38. However, it should be understood that in other exemplary embodiments of this disclosure, the aircraft 10 may additionally or alternatively include any other suitable configuration. For example, in other embodiments, the aircraft 10 may include stabilizers of any other configuration.

[0025] Still referencing Figure 2 and Figure 3 , Figure 1 The exemplary aircraft 10 also includes a propulsion system 50 having a first thruster assembly 52 and a second thruster assembly 54. Figure 2 A schematic cross-sectional view of the first thruster assembly 52 is provided, and Figure 3 A schematic cross-sectional view of the second thruster assembly 54 is provided. As shown, each of the first thruster assembly 52 and the second thruster assembly 54 is configured as an underwing-mounted thruster assembly.

[0026] Special reference Figure 1 and Figure 2 The first thruster assembly 52 is mounted or configured to be mounted on the first side 24 of the aircraft 10, or more specifically, on the first wing 20 of the aircraft 10. The first thruster assembly 52 generally includes a turbine 102 and a main fan (see reference 102). Figure 2(Simply referred to as "fan 104"). More specifically, in the described embodiment, the first thruster assembly 52 is configured as a turbofan engine 100 (i.e., the turbine 102 and fan 104 are configured as part of the turbofan 100).

[0027] like Figure 2 As shown, the turbofan 100 defines an axial direction A1 (extending parallel to the longitudinal centerline 101 provided for reference) and a radial direction R1. As previously described, the turbofan 100 includes a fan 104 and a turbine 102 disposed downstream of the fan 104.

[0028] The exemplary turbine 102 described generally includes a substantially tubular housing 106 defining an annular inlet 108. The housing 106 encloses, in a series flow relationship, a compressor section including a boost or low-pressure (LP) compressor 110 and a high-pressure (HP) compressor 112; a combustion section 114; a turbine section including a first, low-pressure (LP) turbine 118 and a second, high-pressure (HP) turbine 116; and an exhaust nozzle section 120.

[0029] The exemplary turbine 102 of the turbofan 100 also includes one or more shafts that can rotate with at least a portion of the turbine section, and in the described embodiment, the one or more shafts can rotate with at least a portion of the compressor section. More specifically, in the described embodiment, the turbofan 100 includes a high-pressure (HP) shaft or spool 122 that drivesly connects the high-pressure turbine 116 to the high-pressure compressor 112. Furthermore, the exemplary turbofan 100 includes a low-pressure (LP) shaft or spool 124 that drivesly connects the low-pressure turbine 118 to the low-pressure compressor 110.

[0030] Furthermore, the described exemplary fan 104 is configured as a variable pitch fan having a plurality of fan blades 128 spaced apart and connected to the disk 130. As will be understood, the fan 104 includes a total number (i.e., count) of fan blades 128 and defines a fan diameter 126. The fan diameter 126 refers to a measurement twice the radius of the fan blades 128, which is a measurement along the radial direction R1 from the tip of the fan blade 128 to the longitudinal centerline axis 101.

[0031] Fan blades 128 extend outward from disk 130 in a generally radial direction R1. Each fan blade 128 is rotatable relative to disk 130 about a corresponding pitch axis P1 because the fan blades 128 are operatively coupled to a suitable actuating member 132 configured to collectively change the pitch of the fan blades 128. Fan 104 is mechanically coupled to low-pressure shaft 124, thereby being mechanically driven by first, low-pressure turbine 118. More specifically, fan 104, including fan blades 128, disk 130, and actuating member 132, is mechanically coupled to LP shaft 124 via power gearbox 134 and can rotate about longitudinal axis 101 through LP shaft 124. Power gearbox 134 includes multiple gears for reducing the rotational speed of LP shaft 124 to a more efficient fan rotational speed. Thus, fan 104 is powered by the LP system of turbine 102 (including LP turbine 118).

[0032] Still refer to Figure 2 In an exemplary embodiment, the disk 130 is covered by a rotatable front hub 136 having an aerodynamic shape to facilitate airflow through a plurality of fan blades 128. Furthermore, the turbofan 100 also includes an annular fan housing or outer nacelle 138 that circumferentially surrounds at least a portion of the fan 104 and / or turbine 102. Therefore, the described exemplary turbofan 100 may be referred to as a “duct-type” turbofan engine. Additionally, the nacelle 138 is supported relative to the turbine 102 by a plurality of circumferentially spaced outlet guide vanes 140. A downstream section 142 of the nacelle 138 extends to the exterior of the turbine 102 to define a bypass airflow passage 144 therebetween.

[0033] Still refer to Figure 2 The propulsion system 50 also includes an electric motor, which, in the described embodiment, is configured as a generator 56. In the described embodiment, the generator 56 is located within the turbine 102 of the turbofan engine 100 and is mechanically connected to a shaft of the turbofan engine 100. More specifically, in the described embodiment, the generator is driven by a first, low-pressure turbine 118 via a low-pressure shaft 124. The generator 56 is configured to convert the mechanical power of the low-pressure shaft 124 into electrical power. Therefore, the generator 56 is also powered by the low-pressure system of the turbine 102 (including the low-pressure turbine 118).

[0034] However, it should be understood that in other exemplary embodiments, generator 56 may alternatively be located in any other suitable location or elsewhere within turbine 102, and may, for example, be powered in any other suitable manner. For example, in other embodiments, generator 56 may be coaxially mounted with or offset from the low-pressure shaft 124 within the turbine section and driven by a suitable gear set. Furthermore, or alternatively, in other exemplary embodiments, generator 56 may be powered by a high-pressure system, i.e., by the high-pressure turbine 116 via the high-pressure shaft 122, or by both the low-pressure system (e.g., low-pressure shaft 124) and the high-pressure system (e.g., high-pressure shaft 122) via a dual-drive system.

[0035] What should be further understood is that Figure 2 The exemplary turbofan engine 100 described herein may have any other suitable configuration in other exemplary embodiments. For example, in other exemplary embodiments, fan 104 may not be a variable pitch fan, and further, in other exemplary embodiments, LP shaft 124 may be directly mechanically coupled to fan 104 (i.e., turbofan engine 100 may not include gearbox 134). Furthermore, it should be understood that in other exemplary embodiments, turbofan engine 100 may be used instead of being configured as any other suitable aircraft engine, including a turbine mechanically coupled to a main fan. For example, in other embodiments, turbofan engine 100 may be used instead of being configured as a turboprop engine (i.e., the main fan may be configured as a propeller), a non-ducted turbofan engine (i.e., a gas turbine engine may not include external nacelle 138), and so on.

[0036] Still refer to Figure 1 and Figure 2The described propulsion system 50 also includes a power bus 58 to allow the generator 56 to be electrically connected to the propulsion system 50 and / or one or more other components of the aircraft 10. In the described embodiment, the power bus 58 includes one or more wires 60 connected to the generator 56, and in the described embodiment, the one or more wires 60 extend through one or more outlet guide vanes 140. Furthermore, the described propulsion system 50 further includes one or more energy storage devices 55 (such as one or more batteries or other electrical energy storage devices) electrically connected to the power bus 58 for, for example, supplying power to the fan assembly 54 and / or receiving power from the generator 56. In some exemplary embodiments, the one or more energy storage devices 55 may be positioned close to the fan assembly 54 for weight distribution purposes. Including one or more energy storage devices 55 can provide performance gains and can increase the propulsion capability of the propulsion system 50, for example, during transient operation. More specifically, a propulsion system 50 including one or more energy storage devices 55 can respond more rapidly to speed change demands.

[0037] Now for special reference Figure 1 and Figure 3 The exemplary propulsion system 50 also includes a second thruster assembly 54, which is positioned or configured to be positioned spaced apart from the first thruster assembly 52 (including, for example, a turbine and a main fan). More specifically, in the described embodiment, the second thruster assembly 54 is mounted laterally away from the first thruster assembly 52, such that they take in different airflows in the lateral direction L. However, in other embodiments, the first thruster assembly 52 and the second thruster assembly 54 may each be mounted to the aircraft 10 using a common bracket. However, with such a configuration, the first thruster assembly 52 and the second thruster assembly 54 can still be positioned on the bracket, for example, spaced apart from each other in the lateral direction L, so that they take in different airflows in the lateral direction L.

[0038] Still refer to Figure 1 and Figure 3 In an exemplary embodiment, the second thruster assembly 54 is mounted on the second side 26 of the aircraft 10, or in other words, on the second wing 22 of the aircraft 10. (See also: Special Reference) Figure 3The second thruster assembly 54 is generally configured as a fan assembly, which includes a fan 200. The fan 200 defines an axial direction A2 extending along a longitudinal centerline axis 202, through which it is referenced, and a radial direction R2. Furthermore, the fan 200 generally includes a fan 204 and a motor, which, in the described embodiment, is configured as a motor 206. In the described embodiment, the fan 204 is rotatable about the centerline axis 202.

[0039] Fan 204 includes a plurality of fan blades 208 and a fan shaft 210. The plurality of fan blades 208 are attached to / rotatable with the fan shaft 210 and are spaced apart generally along the circumferential direction of the electric fan 200 (not shown). More specifically, fan 204 of electric fan 200 generally includes a total number of fan blades 208 and defines a fan diameter 211. The fan diameter 211 refers to a measurement twice the radius of the fan blades 208, which is a measurement along the radial direction R2 from the tip of the fan blade 208 to the longitudinal centerline axis 22.

[0040] In some exemplary embodiments, the plurality of fan blades 208 may be fixedly attached to the fan shaft 210, or alternatively, the plurality of fan blades 208 may be rotatable relative to the fan shaft 210, as in the described embodiment. For example, each of the plurality of fan blades 208 defines a corresponding pitch axis P2, and in the described embodiment, they are attached to the fan shaft 210 such that the pitch of each of the plurality of fan blades 208 can be uniformly changed, for example, by a pitch changing mechanism 211. Changing the pitch of the plurality of fan blades 208 can improve the efficiency of the second thruster assembly 54 and / or can allow the second thruster assembly 54 to achieve a desired thrust profile. With such exemplary embodiments, the fan 204 may be referred to as a variable pitch fan.

[0041] Furthermore, in the described embodiment, the described electric fan 200 also includes a fan housing or outer nacelle 212, which is attached to the core 214 of the electric fan 200 by one or more struts or outlet guide vanes 216. In the described embodiment, the outer nacelle 212 substantially completely surrounds the fan 204, particularly the plurality of fan blades 208. Therefore, in the described embodiment, the electric fan 200 can be referred to as a ducted electric fan.

[0042] Still for special reference Figure 3The fan shaft 210 is mechanically connected to the electric motor 206 within the core 214, such that the electric motor 206 drives the fan 204 via the fan shaft 210. In the described embodiment, the electric motor 206 is configured as a variable-speed motor, so that the electric motor 206 can drive the fan 204 at various rotational speeds regardless of the electrical force supplied to it. Furthermore, in the described embodiment, the electric fan 200 also includes a gearbox 215, which allows the rotational speed of the fan shaft 210 to be further increased or decreased relative to the rotational speed of the electric motor 206. Therefore, in the described embodiment, the electric motor 206 further drives the fan 204 through the gearbox 215 and via the fan shaft 210.

[0043] The fan shaft 210 is supported by one or more bearings 218, such as one or more roller bearings, ball bearings, or any other suitable bearings. Furthermore, the motor 206 can be an inner rotor motor (i.e., including a rotor radially inside the stator) or an outer rotor motor (i.e., including a stator radially inside the rotor). As briefly described above, the generator 56 of the propulsion system 50 is electrically connected to the electric fan 200 to supply power to the electric fan 200. More specifically, the motor 206 of the electric fan 200 is electrically connected to a power bus 58, which, in the described embodiment, includes one or more wires 60 electrically connected to the motor 206. Thus, the motor 206 is more specifically electrically connected to the power bus 58 via one or more wires 60, and the power bus 58 can supply power to the motor 206 to drive the motor 206, and subsequently drive the fan 204.

[0044] For a brief reference again Figure 1 The described propulsion system 50, or the described power bus 58, also includes an electrical controller 62. The described exemplary generator 56 is electrically connected to the electric fan 200 via the electrical controller 62 of the power bus 58. The electrical controller 62 may be operatively connected to one or more additional controllers of the aircraft to control the electrical power supplied to the electric fan assembly.

[0045] Furthermore, it should be understood that in some exemplary embodiments, the fan 204 of the electric fan 200 may differ from the fan 104 of the turbofan engine 100. More specifically, at least one of the fan diameter 126 or the total number of fan blades 128 of the fan 104 of the turbofan engine 100 may differ from the fan diameter 211 or the total number of fan blades 208 of the fan 204 of the electric fan assembly. Additionally, or alternatively, in other exemplary embodiments, during operation of the respective fan at rated speed, the fan 104 of the turbofan engine may define a fan pressure ratio different from that of the fan 204 of the electric fan 200. As used herein, the term "fan pressure ratio" refers to the ratio of air pressure immediately downstream of the fan to air pressure immediately upstream of the respective fan. Furthermore, the term "rated speed," as used herein, with respect to the electric fan 200 and the turbofan engine 100, refers to the maximum rotational speed that the electric fan 200 and the turbofan engine 100 can achieve during normal operation. For example, the electric fan 200 and the turbofan engine 100 can operate at their respective rated speeds during maximum load operation, such as during takeoff operation.

[0046] Given that the first thruster assembly is configured as a turbofan engine mounted on the first side of the aircraft, and the second thruster assembly is configured as an electrically driven fan mounted on the second side of the aircraft, the propulsion system according to one or more of the above embodiments may be referred to as a gas-electric or hybrid propulsion system. Such a configuration allows a single, relatively large engine to power two or more thrusters (which may be configured as, for example, fans, propellers, etc.). Therefore, the propulsion system according to one or more embodiments of this disclosure can allow for the inclusion of a relatively large engine, which in turn can allow for improved engine efficiency (compared to relatively smaller engines).

[0047] However, it should be understood that in other embodiments, the fan assembly may include a fan 200 having any other suitable configuration. For example, in other embodiments, the fan 200 may be configured without an external nacelle 212 (i.e., configured as a non-ducted fan). Therefore, it should be understood that in some exemplary embodiments, the fan assembly may include a non-ducted fan.

[0048] Furthermore, in other embodiments, this exemplary propulsion system can be integrated into the aircraft 10 in any other suitable manner. For example, now referring to... Figure 4 The present disclosure describes an aircraft 10 and a propulsion system 50 according to another exemplary embodiment of the present disclosure. Figure 4 The exemplary aircraft 10 and propulsion system 50 can be coupled with Figures 1 to 3The exemplary aircraft 10 and propulsion system 50 are constructed in essentially the same way, therefore, the same or similar numbers may refer to the same or similar parts.

[0049] For example, Figure 4 The exemplary aircraft 10 generally includes a fuselage 12 and a wing assembly comprising a port wing 20 and a starboard wing 22. Furthermore, the propulsion system 50 includes a first propulsion system 52, which includes a turbine and a fan, the turbine and fan being configured, for example, as part of a turbofan engine. The propulsion system 50 also includes a generator 56 mechanically driven by the turbine (see...). Figure 2 Furthermore, the propulsion system 50 includes a second propulsion assembly 54, which is an electric fan assembly. A generator 56 is electrically connected to the electric fan assembly and supplies power to it.

[0050] However, it is worth noting that, for Figure 4 In one embodiment, the electric fan assembly includes a plurality of electric fans 200. More specifically, Figure 4 The electric fan assembly includes a first electric fan 200A mounted on the port wing 20 of the aircraft 10, which is located laterally outside the fuselage 12 relative to the turbofan engine 100. Figure 4 The electric fan assembly further includes a second electric fan 200B mounted on the starboard wing 22 and a third electric fan 200C also mounted on the starboard wing 22. The second electric fan 200B and the third electric fan 200C are spaced apart along the lateral direction L of the aircraft 10. Therefore, for Figure 4 In an exemplary embodiment, the fan assembly includes a plurality of fans 200, which includes at least two fans 200, and more specifically, for the depicted embodiment, includes at least three fans 200. However, it is worth noting that in other exemplary embodiments, the fan assembly may include any other suitable number of fans 200. For example, in other exemplary embodiments, the fan assembly may include two fans 200, four fans 200, or any other suitable number of fans 200. Furthermore, the plurality of fans 200 may be arranged in any other suitable manner and attached to the aircraft 10 (including the tail-mounted configuration) at any suitable location.

[0051] Furthermore, in the described embodiment, the plurality of electric fans 200 can be at least partially powered by a power source. This power source includes a plurality of batteries 55, and the plurality of batteries 55 are connected to… Figure 4The power bus 58 described herein is electrically connected and further electrically connected to the generator 56 (not shown) of the first thruster 52. The generator 56 can provide power / charging for the battery, power directly to one or more electric fans 200 via the power bus 58, or both. Additionally, the power supply includes multiple controllers 62.

[0052] Now for reference Figure 5 A close-up view of a power supply 300 according to exemplary embodiments of the present disclosure is provided. For example, in some exemplary embodiments, Figure 5 The power supply 300 can be similar to the one mentioned above. Figure 4 The power supply 300 is constructed in the manner described.

[0053] As shown in the figure, the power supply 300 includes a battery 302 and a power regulator 304. The power regulator 304 includes a converter 306 electrically connected to the battery 302 and a controller 308 operably connected to the converter 306. More specifically, for the illustrated embodiment, the power supply 300 includes a plurality of batteries 302 and a corresponding plurality of power regulators 304. More specifically, also for the illustrated embodiment, the battery 302 is a first battery 302A, and the power regulator 304 is a first power regulator 304A (thus, the converter 306 is a first converter 306A, and the controller 308 is a first controller 308A). Further for the described embodiment, the power supply 300 further includes a second battery 302B and a second power regulator 304B, the second power regulator 304B having a second converter 306B electrically connected to the second battery 302B and a second controller 308B operably connected to the second converter 306B.

[0054] In the illustrated embodiment, the first battery 302A and the first power regulator 304A are electrically connected to the power bus 310 (similar to bus 58), and similarly, the second battery 302B and the second power regulator 304B are also electrically connected to the power bus 310. In this way, the first battery 302A and the second battery 302B can supply power to the load 312 via the power bus 310, can receive power from the power bus 310 to charge the first battery 302A and the second battery 302B, or both.

[0055] In some exemplary embodiments, the load 312 may be an electric or hybrid electric propulsion unit (e.g., as shown in reference above). Figures 1 to 4 In the described embodiments, it could be an aircraft system load, etc.

[0056] Understandably, although Figure 5While a single load 312 is described, in other exemplary embodiments, the power supply 300 can provide power to any suitable number and type of load. For example, the power supply 300 can be configured to supply power to... Figure 1 The second thruster assembly 54 described in the text Figure 4 The multiple electric fans 200 described herein provide power.

[0057] In this way, it can be understood that battery 302 can be a relatively powerful battery 302 capable of providing a relatively large amount of power to load 312 (or multiple loads 312). For example, in some exemplary embodiments, each battery 302 may define a maximum power output of at least 200 volts (V). Alternatively, in other embodiments, each battery 302 may define a maximum power output of at least 250 volts, at least 300 volts, at least 400 volts, at least 500 volts, and up to, for example, 5000 volts. Each battery 302 may define substantially the same maximum power output.

[0058] However, it is worth noting that each of the plurality of batteries 302, more specifically, the first battery 302A and the second battery 302B, may define different states of charge (i.e., battery charge levels). For example, the first battery 302A may define a first state of charge that differs from the second state of charge defined by the second battery 302B. When the two batteries defining different states of charge are electrically connected to the load 312, the battery 302 with the lower state of charge may draw a higher current and therefore may be consumed faster than the battery 302 with the higher state of charge. Generally, it is desirable to maintain the batteries 302 with substantially the same state of charge to ensure the required system performance. This is especially true in propulsion systems, such as in aerospace propulsion systems.

[0059] Now for reference Figure 6 The diagram depicts a schematic representation of a power supply 300 according to an exemplary embodiment of the present disclosure, the power supply 300 having one or more features for standardizing the state of charge of a plurality of batteries 302. In some embodiments, Figure 6 The power supply 300 depicted in the image can be similar to the one described in the reference above. Figure 5 The exemplary power supply 300 described above. For example... Figure 6 The power supply 300 generally includes a first battery 302A and a second battery 302B, as well as a first power regulator 304A and a second power regulator 304B. In the illustrated embodiment, the first battery 302A and the second battery 302B are arranged in parallel and electrically connected to the load 312.

[0060] The first power regulator 304A generally includes a first converter 306A electrically connected to the first battery 302A and a first controller 308A operably connected to the first converter 306A. Similarly, the second power regulator 304B generally includes a second converter 306B electrically connected to the second battery 302B and a second controller 308B operably connected to the second converter 306B. The first controller 308A is configured to instruct the first converter 306A to modify the power supplied from the first battery 302A to the load 312 by normalizing the state of charge of the first battery 302A using the state of charge of the second battery 302B. Similarly, the second controller 308B is configured to instruct the second converter 306B to modify the power supplied from the second battery 302B to the load 312 by normalizing the state of charge of the second battery 302B using the state of charge of the first battery 302A.

[0061] For example, as will be explained in detail below, controllers 308A and 308B are each configured to, in at least some cases, draw more power from a battery 302 having a higher state of charge than a battery 302 having a lower state of charge. This concept is referred to herein as dynamic droop control. A droop control system can control the power output of a battery by applying a droop resistance in the droop control circuit to provide a more consistent power output across the battery's state of charge range. This disclosure further includes dynamically controlling the droop resistance in certain situations (e.g., below high power requirements) to normalize the state of charge of multiple batteries.

[0062] It is worth noting that in the illustrated embodiment, the first controller 308A and the second controller 308B are communicatively isolated from each other. In this way, it can be understood that the normalization of the state of charge of the first battery 302A in the second battery 302B is accomplished without communication between the first controller 308A and the second controller 308B and / or between the first converter 306A and the second converter 306B, but rather based on locally sensed quantities. As used herein, the term "locally sensed" with respect to a particular controller 308 and / or converter 306 refers to a quantity / parameter sensed upstream of the circuitry including the corresponding battery, where the circuitry encounters the power bus 310.

[0063] The operation of this exemplary system will now be described in more detail with reference to the first battery 302A and the first power regulator 304A. Still referring to... Figure 6It is understood that the power supply 300 includes various sensors for sensing current and voltage flowing through corresponding circuits. For example, the power supply 300 includes a first battery current sensor 314 for sensing current from the first battery 302A, a first battery voltage sensor 316 for sensing the voltage of power supplied from the first battery 302A, a first load current sensor 318 for sensing current flowing to the load 312, and a first load voltage sensor 320 for sensing the voltage of power supplied to the first load 312. Furthermore, the power supply 300 includes a first state of charge circuit 322 for determining a first state of charge of the first battery 302A based on data sensed from the first battery current sensor 314 and the first battery voltage sensor 316. It is understood that, although not explicitly labeled, the power supply 300 includes similar sensors for the circuitry of the second battery 302B for the described exemplary power supply 300.

[0064] Still referencing Figure 6 And now also referencing Figure 7 A close-up schematic diagram of the first controller 308A is provided. From the discussion herein, it can be understood that the first power regulator 304 is configured to receive various local sensing measurements from, for example, first battery sensors 314, 316, 318, 320 and sub-circuit 322, and to control the power output from the first battery 302A to the load 312 so that the state of charge of the first battery 302A is normalized with that of the other batteries 302 of the power supply 300 (i.e., with battery 302B in the illustrated embodiment).

[0065] Specifically, it is understood that, for the illustrated embodiment, the controller 308 generally includes a compensation trigger circuit 324, a dynamic droop control circuit 326, and a voltage regulator droop circuit 328.

[0066] Referring specifically to compensation trigger circuit 324, compensation trigger circuit 324 is configured to receive data indicating the power output from first battery 302A to load 312, more specifically, it is configured to receive data indicating the voltage and current of the power supplied to load 312, each data sourced from first battery 302A. This information may be provided by first load current sensor 318 and first load voltage sensor 320. In block 330, this information is received and used to determine the data indicating the power supplied from first battery 302A to load 312.

[0067] An exemplary compensation trigger circuit 324 passes power output data from block 330 through power filter 332, and then determines in block 334 whether the power output is above a predetermined upper threshold or below a predetermined lower threshold. In the illustrated embodiment, the predetermined upper threshold is 95% of the maximum power output of the first battery 302A, and the predetermined lower threshold is 90% of the maximum power output of the first battery 302A. However, in other embodiments, these upper and lower thresholds can be set to any other suitable values. Furthermore, in the described embodiment, a gap is defined between the upper and lower thresholds to ensure that the output does not trigger back and forth when the power output is exactly on the boundary of one of these thresholds.

[0068] The compensation trigger circuit 324 is configured at block 338 to determine a compensation trigger value based on the power output of battery 302 and to provide the compensation trigger value as an output. More specifically, if the power output is higher than a predetermined upper threshold, the compensation trigger circuit 324 provides a first compensation trigger value, and if the power output is lower than a predetermined lower threshold, the compensation trigger circuit 324 provides a second compensation trigger value. The first and second compensation trigger values ​​can be "TRUE" and "FALSE" values, "1" and "0" values, etc.

[0069] The compensation trigger value output from block 338 is then provided to the dynamic droop control circuit 326. The dynamic droop control circuit 326 is configured to receive the compensation trigger value at switching block 340 and, at least in part, switch the output droop value of the dynamic control circuit from the upper output droop measurement value to the lower output droop measurement value based on the compensation trigger value. For the illustrated embodiment, the upper output droop measurement value is based on a baseline droop resistance set at block 342, while the lower output droop measurement value is based on the state of charge (SOC) of the first battery 302A, calculated at block 344 using the SOC of the first battery 302A. More specifically, for the illustrated embodiment, the lower output droop measurement value is based on a lookup table at block 344, and the value returned from the lookup table is based on the SOC of the battery 302. However, it is understood that in some exemplary aspects, the lower output droop measurement value may additionally be based on other parameters, such as the available power margin of the converter (e.g., the first converter 306A, described below).

[0070] More notably, a brief reference Figure 8 An example lookup table of this disclosure, usable at block 344, is provided. As will be understood, the lookup table includes example variations of droop resistance along its Y-axis 346, based on the state of charge of the first battery 302A along its X-axis 348. As will be understood, the lower output droop measurement returned from the lookup table (the % variation of the droop resistance measurement for the illustrated embodiment) is non-linear over the range of the state of charge of the first battery 302A.

[0071] Now back Figure 7 It is understood that the droop resistance is output from the dynamic droop control circuit 326 at 350. Based on the position of the switching block 340, the droop resistance is calculated either by the upper output droop measurement of the filter 352 (based on the output of block 342) or by the lower output droop measurement of the filter 352 (based on the output of block 344). It is understood that the terms "upper" and "lower," as used herein with respect to the upper and lower output droop measurements, are merely to distinguish between the two measurements and do not imply any relative values, etc.

[0072] As further described, a droop resistor is output at 350 and provided to a voltage regulator droop circuit 328, which uses the output droop value to determine the voltage reference supplied from the first battery 302A to the load 312 at 354. More specifically, the voltage regulator droop circuit 328 receives the current supplied from the first battery 302A to the load 312 and the output droop value, which is also the droop resistor, at block 356, and sets the reference voltage supplied from the first battery 302A to the load 312 through a series of additional blocks, filters, etc.

[0073] Also refer to Figure 6 At 354, the reference voltage output from the voltage regulator droop circuit 328 is provided to the first converter 306A, and the first converter 306A is configured to receive power from the first battery 302A and modify the power supplied from the first battery 302A to match the output of the voltage regulator droop circuit 328 in order to provide the required power to the load 312.

[0074] It is worth noting that, in the illustrated embodiment, the first converter 306A is a DC-to-DC converter 306 (i.e., a direct current to direct current converter 306).

[0075] It is understood that in other exemplary embodiments, the voltage regulator droop circuit 328 may have other suitable configurations, and similarly, the first converter 306A may have any suitable configuration to provide the aforementioned functionality.

[0076] In this way, it can be understood that the first controller 308A is generally configured to determine how much power to supply to the load 312. If the power is relatively high (e.g., above an upper threshold), the dynamic droop control circuit 326 provides an upper output droop measurement based on the baseline droop resistance at block 342, through filter 352. In contrast, if the power supplied to the load 312 is relatively low (e.g., below a lower threshold), the dynamic droop control circuit 326 provides a lower output droop measurement based on a lookup table at block 344 and the first state of charge, through droop filter 352. In this way, if a relatively high power is required, the controller 308 does not provide dynamic droop control, but instead prioritizes providing the required power output. In contrast, if a relatively low power is required, the controller 308 provides dynamic droop control that is non-linear across the span of the state of charge of the first battery 302A to allow the state of charge of multiple batteries 302 to be normalized. More specifically, by using such a configuration, dynamic droop control draws more power from battery 302, which has a higher state of charge than a battery with a lower state of charge.

[0077] Still refer to Figure 6 It will be further understood that the exemplary power supply 300, schematically depicted, includes a similar configuration for a second battery circuit (connecting the second battery 302B to the power bus 310 and the load 312). More specifically, as described above, the power supply 300 further includes a second power regulator 304B, which includes a second converter 306B electrically connected to the second battery 302B and a second controller 308B operatively connected to the second converter 306B. The second controller 308B may be constructed in substantially the same manner as the first controller 308A, as referenced above. Figure 7 A more detailed description is provided. For example, the second controller 308B may include a second compensation trigger circuit (not shown, similar to 324) configured to provide a second compensation trigger value based on the power output of the second battery 302B, and a second dynamic droop control circuit (not shown, similar to 326) configured to receive the second compensation trigger value and switch the output droop value of the second dynamic control circuit from an upper output droop measurement value to a lower output droop measurement value. The lower output droop measurement value of the dynamic droop control circuit may be based on a second state of charge of the second battery 302B. For example, similar to the description above, see reference to... Figure 7 and Figure 8 The described construction allows the output droop measurement of the dynamic droop control circuit to be based on a lookup table that is based on the second state of charge of the second battery 302B. The lookup table used for the second dynamic control loop can be the same as the lookup table used for the first dynamic control loop, or it can be a different lookup table.

[0078] Furthermore, the second controller 308B may further include a second voltage regulator droop circuit 328, which utilizes the output droop value of the second dynamic droop control circuit 326.

[0079] In this way, it can be understood that two or more batteries 302 (or each battery 302) can employ selective dynamic droop control to more effectively normalize the state of charge of the batteries 302 without requiring operational connectivity between the respective controllers 308, converters 306, etc.

[0080] Now for reference Figure 9 A flowchart of a method 400 for operating a power source is provided. This method 400 can be used as described above. Figures 1 to 8 One or more exemplary power supplies are described. Additionally, in other exemplary embodiments, Figure 9 The exemplary method 400 can be used with any other suitable power supply.

[0081] The method 400 includes, at (402), determining the power output of a battery defining a state of charge, and at (404), determining a compensation trigger value based on the power output of the battery determined at (402). In at least some exemplary aspects, determining the compensation trigger value based on the power output of the battery determined at (404) includes, at (405), determining that the power output of the battery is below a lower limit power output threshold, and setting the compensation trigger value accordingly.

[0082] Further, method 400 includes (406) switching the output droop value from the upper output droop measurement value to the lower output droop measurement value based on a determined compensation trigger value, wherein the lower output droop measurement value is based on the state of charge of the battery.

[0083] As in the embodiments described above, the upper output droop measurement can be based on the baseline droop resistance.

[0084] Still referencing Figure 9 For the described exemplary aspects, switching the output droop value from an upper output droop measurement to a lower output droop measurement at (406) includes determining the lower output droop measurement at (408) based on a lookup table that is based on the battery's state of charge. In at least one of these exemplary aspects, the lower output droop measurement is non-linear over the range of the battery's state of charge.

[0085] The method 400 further includes, at (410), using a voltage regulator droop circuit of the controller to determine a reference output voltage, the voltage regulator droop circuit utilizing the output droop value of a dynamic droop control circuit. The method 400 also includes, at (412), using a converter electrically connected to the controller to modify the battery's power output, and more specifically, using a converter electrically connected to the controller to modify the battery's power output based on the reference output voltage determined at (410).

[0086] Furthermore, it is understood that, in at least some exemplary aspects, the method 400 described herein can be used with multiple batteries. For example, in some exemplary embodiments, the battery may be a first battery, the state of charge may be a first state of charge, and the method 400 may further include: at (414), determining a second power output of a second battery defining a second state of charge; at (416), determining a second compensation trigger value based on the second power output of the second battery determined at (414); and at (418), switching a second output droop value from an upper output droop measurement value to a lower output droop measurement value based on the determined second compensation trigger value. Using such exemplary aspects, the lower output droop measurement value may be based on the second state of charge of the battery (e.g., using a lookup table). It is noteworthy that steps (414), (416), and (418) may occur in parallel with the preceding method steps.

[0087] This written description uses examples to disclose the invention, including the best mode, and also enables any person skilled in the art to practice the invention, including making and using any device or system and performing any combination of methods. The patentable scope of the invention is defined by the claims and may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not different from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0088] Further details of this disclosure are set forth in the following terms:

[0089] A power source, characterized in that it comprises: a battery defining a state of charge; a converter electrically connected to the battery; and a controller operatively connected to the converter, the controller comprising: a compensation trigger circuit configured to provide a compensation trigger value based on the power output of the battery; and a dynamic droop control circuit configured to receive the compensation trigger value and switch the output droop value of the dynamic droop control circuit from an upper output droop measurement value to a lower output droop measurement value, wherein the lower output droop measurement value is based on the state of charge of the battery.

[0090] According to one or more of these terms, the power source, wherein the upper output droop measurement is based on the baseline droop resistance.

[0091] According to one or more of these terms, the power source, wherein the lower output droop measurement is based on a lookup table, which is based on the battery's state of charge.

[0092] According to one or more of these terms, the power source, wherein the lower output droop measurement is non-linear within the range of the battery's state of charge.

[0093] According to one or more of these provisions, the controller further includes a voltage regulator droop circuit that utilizes the output droop value of a dynamic droop control circuit.

[0094] A power source according to one or more of these terms, wherein the battery is a first battery, wherein the state of charge is a first state of charge, wherein the converter is a first converter, wherein the controller is a first controller, and wherein the power source further includes: a second battery defining a second state of charge; a second converter electrically connected to the second battery; and a second controller operatively connected to the second converter, the second controller including: a second compensation trigger circuit configured to provide a second compensation trigger based on the power output of the second battery; and a second dynamic droop control circuit configured to receive the second compensation trigger value and switch the output droop value of the second dynamic droop control circuit from an upper output droop measurement value to a lower output droop measurement value, wherein the lower output droop measurement value is based on the second state of charge of the second battery.

[0095] According to one or more of these terms, the power source, wherein the output droop value of the second dynamic droop control circuit is based on a lookup table, which is based on the second state of charge of the second battery.

[0096] The power source is provided in accordance with one or more of these terms, wherein the first controller and the second controller are communicatively isolated from each other.

[0097] A power source according to one or more of these provisions, wherein the first controller includes a first voltage regulator droop circuit utilizing the output droop value of a first dynamic droop control circuit, and wherein the second controller includes a second voltage regulator droop circuit utilizing the output droop value of a second dynamic droop control circuit.

[0098] According to one or more of these terms, the power source, wherein the first battery and the second battery are electrically connected to a common load.

[0099] According to one or more of these provisions, the power source wherein the compensation trigger circuit is configured to provide a compensation trigger value equal to a first output when the power output is above an upper threshold, and to provide a compensation trigger value equal to a second output when the power output is below a lower threshold.

[0100] According to one or more of these provisions, the power source wherein the dynamic droop control circuit is configured to switch the output droop value of the dynamic droop control circuit from the upper output droop measurement value to the lower output droop measurement value when the compensation trigger value is equal to the second output.

[0101] A power source according to one or more of these terms, wherein the power source is used for propulsion system.

[0102] A power source according to one or more of these terms, wherein the power source is used for an aircraft propulsion system.

[0103] The power source is subject to one or more of these terms, wherein the maximum power output of the first battery is limited to at least 250 volts.

[0104] According to one or more of these terms, the power source, wherein the first battery is defined to have a maximum power output of at least 500 volts and up to 5000 volts.

[0105] The power source is subject to one or more of these terms, wherein the converter is a DC-to-DC converter.

[0106] A method of operating a power source includes: determining the power output of a battery with a defined state of charge; determining a compensation trigger value based on the determined power output of the battery; and switching an output droop value from an upper output droop measurement value to a lower output droop measurement value based on the determined compensation trigger value, wherein the lower output droop measurement value is based on the state of charge of the battery.

[0107] According to the method of one or more of these terms, the upper output droop measurement is based on the baseline droop resistance.

[0108] The method according to one or more of these terms, wherein switching the output droop value from an upper output droop measurement to a lower output droop measurement includes determining the lower output droop measurement based on a lookup table, the lookup table being based on the battery's state of charge.

[0109] According to the method of one or more of these provisions, the lower output droop measurement is non-linear within the range of battery state of charge.

[0110] The method according to one or more of these provisions further includes using a voltage regulator droop circuit of the controller to determine a reference output voltage, the voltage regulator droop circuit utilizing the output droop value of a dynamic droop control circuit; and using a converter electrically connected to the controller to modify the battery's power output.

[0111] The method according to one or more of these terms, wherein the battery is a first battery, wherein the state of charge is a first state of charge, and wherein the method further includes determining a second power output of a second battery defining a second state of charge; determining a second compensation trigger value based on the determined second power output of the second battery; and switching a second output droop value from an upper output droop measurement value to a lower output droop measurement value based on the determined second compensation trigger value, wherein the lower output droop measurement value is based on the second state of charge of the battery.

[0112] The method according to one or more of these terms, wherein determining the compensation trigger value based on the determined power output of the battery includes determining that the power output of the battery is below a lower threshold.

Claims

1. A controller assembly for a power source, the power source comprising a battery and a converter electrically connected to the battery, characterized in that, The controller component includes: Controller, the controller includes: A compensation trigger circuit, wherein when the controller is capable of operating with the power source, the compensation trigger circuit is configured to provide a compensation trigger value based on data indicating a determined power output of the battery; and A dynamic droop control circuit, wherein when the controller is capable of operating with the power source, the dynamic droop control circuit is configured to receive the compensation trigger value and switch the output droop value of the dynamic droop control circuit from an upper output droop measurement value to a lower output droop measurement value, wherein the lower output droop measurement value is based on the state of charge of the battery.

2. The controller assembly according to claim 1, characterized in that, The aforementioned upper output droop measurement is based on the baseline droop resistance.

3. The controller assembly according to claim 1, characterized in that, The lower output droop measurement is based on a lookup table, which is based on the state of charge of the battery.

4. The controller assembly according to claim 3, characterized in that, Within the range of the state of charge of the battery, the lower output droop measurement value is nonlinear.

5. The controller assembly according to claim 1, characterized in that, Further including A voltage regulator droop circuit, the voltage regulator droop circuit being configured to utilize the output droop value of the dynamic droop control circuit.

6. The controller assembly according to claim 1, characterized in that, The power source's battery is a first battery, the state of charge is a first state of charge, the power source's converter is a first converter, and the power source further includes a second battery defining a second state of charge and a second converter electrically connected to the second battery, the controller is a first controller, and the controller component further includes: A second controller, configured to be operatively connected to the second converter, includes... The second compensation trigger circuit is configured to provide a second compensation trigger value based on the power output of the second battery when the second controller is able to operate with the power source. The second dynamic droop control circuit, wherein when the second controller is able to operate with the power source, the second dynamic droop control circuit is configured to receive the second compensation trigger value and switch the output droop value of the second dynamic droop control circuit from the upper output droop measurement value to the lower output droop measurement value, wherein the lower output droop measurement value is based on the second state of charge of the second battery.

7. The controller assembly according to claim 6, characterized in that, The lower output droop measurement value of the output droop value of the second dynamic droop control circuit is based on a lookup table, which is based on the second state of charge of the second battery.

8. The controller assembly according to claim 6, characterized in that, The first controller and the second controller are communication-isolated from each other.

9. The controller assembly according to claim 6, characterized in that, The first controller includes a first voltage regulator droop circuit that utilizes the output droop value of the first dynamic droop control circuit, and the second controller includes a second voltage regulator droop circuit that utilizes the output droop value of the second dynamic droop control circuit.

10. The controller assembly according to claim 6, characterized in that, The first battery and the second battery are electrically connected to a common load.

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